A btt guidance and control method for near-space hypersonic vehicle

Abstract

The invention discloses a BTT guidance control method for a near-space hypersonic flight vehicle. The guidance control method includes the steps that S1, a combined control model of a rolling channel and a yawing channel is established based on the aileron control quantity of the rolling channel, and a control model of a pitching channel is established based on the pitching control quantity; S2, a nonlinear state equation of BTT guidance is established based on the kinetic parameters of the flight vehicle, and the nonlinear state equation is transformed into a state-dependent linear-like structure; S3, by adopting a Riccati equation control method, a guidance law model of the rolling channel, the yawing channel and the pitching channel of the flight vehicle is obtained according to the state-dependent linear-like structure. The guidance control method solves the problem of multichannel cross coupling in BTT control of the near-space hypersonic flight vehicle and can meet the demand for high-precision control of the near-space hypersonic flight vehicle.

Description

technical field [0001] The invention relates to the field of aircraft guidance. More specifically, it relates to a BTT guidance and control method for a near-space hypersonic vehicle. Background technique [0002] During the re-entry flight of a conventional full-motion rudder maneuvering aircraft, the thermal environment near the rudder gap and the rudder shaft is particularly harsh. The design of the rudder often becomes a serious constraint factor affecting the tactical performance of the aircraft. The successful application of FLAP rudders has solved the problem of rudder ablation overheating, and there have been many successful cases abroad, such as the American HTV-1 aerodynamic shape is a double-cone lift body configuration, and a FLAP rudder is installed at its tail; similar waveriding structures The windward side of the shaped HTV-2 also uses the FLAP rudder as the aerodynamic rudder, and cooperates with the RCS installed at the bottom of the aircraft to control t...

AI Technical Summary

Problems solved by technology

[0003] However, in the BTT guidance and control process of the near-space hypersonic vehicle using the FLAP rudder, the roll angular velocity of the vehicle will inevitably produce a very unfavorable roll-induced moment for the attitude control, and this coupling effect will increase with the roll The increase of the angular velocity brings new difficulties to the design of the guidance control system

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